EP3778379B1 - Mutterplattenanordnung - Google Patents

Mutterplattenanordnung Download PDF

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Publication number
EP3778379B1
EP3778379B1 EP20190055.2A EP20190055A EP3778379B1 EP 3778379 B1 EP3778379 B1 EP 3778379B1 EP 20190055 A EP20190055 A EP 20190055A EP 3778379 B1 EP3778379 B1 EP 3778379B1
Authority
EP
European Patent Office
Prior art keywords
nut
base plate
wing
channel
assembly
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP20190055.2A
Other languages
English (en)
French (fr)
Other versions
EP3778379A1 (de
Inventor
Steven Paul Walker
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Boeing Co filed Critical Boeing Co
Publication of EP3778379A1 publication Critical patent/EP3778379A1/de
Application granted granted Critical
Publication of EP3778379B1 publication Critical patent/EP3778379B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B37/00—Nuts or like thread-engaging members
    • F16B37/04—Devices for fastening nuts to surfaces, e.g. sheets, plates
    • F16B37/044—Nut cages
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B37/00—Nuts or like thread-engaging members
    • F16B37/04—Devices for fastening nuts to surfaces, e.g. sheets, plates
    • F16B37/041—Releasable devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B37/00—Nuts or like thread-engaging members
    • F16B37/04—Devices for fastening nuts to surfaces, e.g. sheets, plates
    • F16B37/045—Devices for fastening nuts to surfaces, e.g. sheets, plates specially adapted for fastening in channels, e.g. sliding bolts, channel nuts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B37/00—Nuts or like thread-engaging members
    • F16B37/14—Cap nuts; Nut caps or bolt caps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
    • F16B5/06—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of clamps or clips
    • F16B5/0607—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of clamps or clips joining sheets or plates to each other
    • F16B5/0621—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of clamps or clips joining sheets or plates to each other in parallel relationship
    • F16B5/0642—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of clamps or clips joining sheets or plates to each other in parallel relationship the plates being arranged one on top of the other and in full close contact with each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B33/00—Features common to bolt and nut
    • F16B33/002—Means for preventing rotation of screw-threaded elements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B33/00—Features common to bolt and nut
    • F16B33/004—Sealing; Insulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B37/00—Nuts or like thread-engaging members
    • F16B37/04—Devices for fastening nuts to surfaces, e.g. sheets, plates

Definitions

  • the subject matter herein relates generally to aircraft assembly.
  • a wing assembly of an aircraft includes wing panels that are secured to wing spars or other internal structures of the wing assembly.
  • Many fasteners are used to secure the wing panel to the wing spar.
  • a nut is held in the interior of the wing assembly while the fastener is fastened from the exterior of the wing assembly.
  • the installer typically needs to access the interior of the wing assembly to position and hold the nut during the fastening process. Assembly of the wing panel to the wing spar is a time-consuming process. Additionally, the interior space of the wing assembly is not easily accessible. Furthermore, as wing assemblies are designed to be thinner, the amount of space for access by the installer is limited.
  • Document US2009/129885A1 in accordance with its abstract, states methods relating to and apparatus such as floating nut plates which include complementary surfaces limiting movement of a retainer toward or away from side walls of a receiver, such as wherein a nut element is positioned between the retainer and the receiver.
  • One of the complementary surfaces may be a groove formed in the retainer.
  • the receiver and/or retainer are non-metal.
  • Document FR2983268A1 in accordance with its abstract, states a device that has branches gripping an edge of a piece and including inner faces and outer faces. Openings allow a screw to pass through the branches. A nut is secured to one of the outer faces and positioned opposite to one of the openings. The nut allows screwing of the screw, and a protection system is formed by a cover being fixed on one of the branches carrying the nut and partially covering the nut and by a rupture zone that allows the cover to be disconnected from the branch when the screw exerts force on the cover.
  • Documemt US3164191A in accordance with its introductory part, states a gang channel of the type wherein a plurality of fastener elements are contained in spaced relationship in a channel member having side flanges perpendicular to a base web having openings therein to facilitate bolt insertion into the fastener elements.
  • a nut plate assembly is provided as per claim 1.
  • base plate has a reinforcement lip at the front edge forming a seal groove.
  • the nut plate assembly includes a base plate seal received in the seal groove configured to seal between the base plate and the mounting structure.
  • a wing assembly is provided according to claim 14.
  • Figure 1 illustrates a perspective front view of an aircraft 110 according to an example of the present disclosure.
  • the aircraft 110 is an example of a vehicle with which a nut plate assembly 100 according to an example of the present disclosure may be utilized.
  • examples of the present disclosure may be used with various other vehicles, such as automobiles, buses, locomotives and train cars, seacraft, spacecraft, and the like.
  • the aircraft 110 includes a propulsion system 112 that may include two turbofan engines 114, for example.
  • the propulsion system 112 may include different engines or more engines 114 than shown.
  • the engines 114 are carried by wing assemblies 116 of the aircraft 110 connected to a fuselage 118 of the aircraft 110.
  • the nut plate assemblies 100 may be used for mechanically connecting together various structures of the wing assemblies 116.
  • the nut plate assemblies 100 may be used on other structures of the aircraft 110, such as for structures of the fuselage 118.
  • the engines 114 may be carried by a fuselage 118 and/or an empennage 120 in other examples.
  • the empennage 120 may also support horizontal stabilizers 122 and a vertical stabilizer 124.
  • the fuselage 118 of the aircraft 110 defines an internal cabin, which includes a cockpit, one or more work sections (for example, galleys, personnel carry-on baggage areas, and the like), one or more passenger sections (for example, first class, business class, and coach sections), and an aft section. Each of the sections may be separated by a cabin transition area.
  • FIG. 2 is a partial sectional view of one of the wing assemblies 116.
  • the wing assembly 116 includes an inner structure and an outer structure.
  • the outer structure includes wing panels 130 forming outer surfaces of the wing assembly 116.
  • the inner structure includes wing spars 132 extending lengthwise at least partially between a root 134 and a tip 136 of the wing assembly 116.
  • the inner structure includes wing ribs 138 extending between the wing spars 132.
  • Various system components of the aircraft 110 may be arranged within the interior of the wing assembly 116.
  • mechanical and electrical components such as for operating wing flaps, may be routed through the inner structure of the wing assembly 116.
  • Components of a fuel system such as fuel tanks, fuel lines, fuel valves and the like may be contained within the inner structure of the wing assembly 116.
  • the wing panels 130 cover and enclose the inner structure and the components of the wing assembly 116.
  • the nut plate assemblies 100 are used to couple various structures of the wing assembly 116.
  • the nut plate assemblies 100 may be used to connect the wing panels 130 to the wing spars 132.
  • the nut plate assemblies 100 hold nuts at proper locations for receiving fasteners, such as threaded fasteners, used to couple together the structures of the wing assembly 116.
  • the fasteners are secured from the exterior surface of the wing assembly 116.
  • the wing panel 130 is positioned over the wing spar 132 to cover and close out the wing assembly 116 restricting access to the inner structure.
  • the nut plate assemblies 100 are arranged within the interior of the wing assembly 116 and the fasteners are coupled to the nut plate assemblies 100 from the exterior surface of the wing panel 130.
  • the nut plate assemblies 100 hold the nuts in position to receive the fasteners without the need for the installer to enter or access the interior of the wing assembly 116.
  • FIG 3 is a top perspective view of the nut plate assembly 100 in accordance with an example positioned relative to mounting structures 150.
  • Figure 4 is a bottom perspective view of the nut plate assembly 100 in accordance with an example positioned relative to the mounting structures 150.
  • the mounting structures 150 may be structures of the aircraft 110 (shown in Figure 1 ) in various examples.
  • the mounting structures 150 include the wing rib 138, the wing spar 132, and the wing panel 130 (the wing panel 130 is removed in Figure 3 to illustrate the nut plate assembly 100).
  • the nut plate assembly 100 is used to mechanically connect the wing panel 130 to the wing spar 132.
  • the nut plate assembly 100 is mounted to the wing rib 138 to position the nut plate assembly 100 relative to the wing spar 132.
  • the nut plate assembly 100 is coupled to a mounting surface of the wing rib 138 proximate to an end of the wing rib 138.
  • the nut plate assembly 100 may be centered over the wing rib 138 with a first portion of the nut plate assembly 100 extending to a first side 140 of the wing rib 138 and a second portion of the nut plate assembly 100 extending to a second side 142 of the wing rib 138.
  • the nut plate assembly 100 is cantilevered in both directions from the wing rib 138.
  • the nut plate assembly 100 may extend mid-bay to mid-bay on opposite sides of the wing rib 138.
  • Other nut plate assemblies 100 may be arranged adjacent to the nut plate assembly 100, such as being coupled to adjacent wing ribs 138 (not shown).
  • the nut plate assembly 100 may be mounted to the wing ribs 138 and loaded into position relative to the wing spar 132 with the wing rib 138. In other examples, the nut plate assembly 100 may be mounted to the wing rib 138 prior to the wing spar 132 being positioned at the wing rib 138. In the illustrated example, the nut plate assembly 100 is mounted to the top of the wing rib 138 and is used to connect the wing panel 130 to a spar flange 144 at the top of the wing spar 132.
  • the nut plate assemblies 100 may additionally or alternatively be used at the bottom of the wing assembly 116, such as to attach a lower wing panel to the lower spar flange of the wing spar 132.
  • the nut plate assembly 100 is provided at an interior of the wing assembly 116 and holds nuts within the interior of the wing assembly 116 for connecting to fasteners (not shown) assembled from an exterior surface of the wing assembly 116, such as from above the wing panel 130.
  • the nut plate assembly 100 includes seals to provide sealing between the nut plate assembly 100 and the mounting structures 150 to seal the interior of the wing assembly 116 from the exterior surface of the wing assembly 116.
  • the seal may be a fuel seal of the wing assembly 116 that prevents leakage of fuel from the inner phase of the wing assembly 116 to the exterior surface of the wing assembly 116.
  • the nut plate assembly 100 provides spark arresting for static discharge, such as from the fasteners to the inner bays of the wing assembly 116.
  • the nut plate assembly 100 has a closed bottom (i.e. a non-conductive nut cap) to cover the fastener passing through the wing panel 130 and the spar flange 144 of the wing spar 132.
  • FIG. 5 is a top perspective view of the nut plate assembly 100 in accordance with an example.
  • the nut plate assembly 100 includes a base plate 200, a plurality of channel fittings 202 coupled to the base plate 200, and nut caps 204 coupled to the channel fittings 202.
  • the base plate 200 holds a base plate seal 206 configured to be sealed against the mounting structures 150 (shown in Figure 4 ).
  • the nut caps 204 hold nuts 208, such as threaded nuts, configured to be coupled to fasteners 210, such as threaded fasteners.
  • the channel fittings 202 are separate and discrete from each other and are separate and discrete from the base plate 200.
  • the channel fittings 202 are arranged periodically in spaced apart relationship along the base plate 200 and separated from each other by gaps 212. Providing multiple channel fittings 202 at spaced apart locations reduces the overall weight of the nut plate assembly 100 to reduce deflection or bending of the base plate 200 during assembly.
  • the channel fittings 202 are adhered to the base plate 200, such as using adhesive. However, the channel fittings 202 may be secured to the base plate 200 by other processes in alternative examples.
  • the base plate 200 is a plate-like structure having a plurality of base plate openings 220 therethrough.
  • the base plate openings 220 are configured to receive the fasteners 210 to secure the base plate 200 to the mounting structures 150 (for example, to join the wing panel 130 in the wing spar 132).
  • the base plate 200 is manufactured from a material having sufficient stiffness to support the channel fittings 202 and the nut caps 204.
  • the base plate 200 may be manufactured from a carbon fiber reinforced plastic material
  • the base plate 200 may be manufactured from a thermoset plastic material or a thermoplastic material.
  • the base plate 200 may be manufactured from a metal material, such as aluminum.
  • the base plate 200 has a top 222 and a bottom 224.
  • the top 222 is configured to face the mounting structure 150 (for example, the base plate 200 is configured to be positioned below the mounting structure 150).
  • the channel fittings 202 are mounted to the bottom 224 of the base plate 200.
  • the base plate 200 extends between a first side 226 and a second side 228.
  • the base plate 200 extends between a front edge 230 and a rear edge 232.
  • the base plate 200 includes a reinforcement lip 234 at the front edge 230 that forms a seal groove 236 that receives the base plate seal 206.
  • the reinforcement lip 234 extends between the first and second sides 226, 228.
  • the reinforcement lip 234 is non-coplanar with the base plate 200.
  • the reinforcement lip 234 extends upward relative to the base plate 200.
  • the reinforcement lip 234 may be a curved lip forming a curved seal groove 236 along the inner surface of the curved lip.
  • the reinforcement lip 234 may be formed by bending the reinforcement lip 234 at an angle relative to the base plate 200, such as perpendicular to the base plate 200.
  • the reinforcement lip 234 provide structural stiffness to the base plate 200 along the length of the base plate 200.
  • the base plate 200 may additionally or alternatively include a reinforcement lip at the rear edge 232.
  • the base plate 200 includes a mounting area 240 generally centered along the length of the base plate 200 between the first side 226 and the second side 228.
  • the base plate 200 includes mounting openings 242 at the mounting area 240.
  • the mounting openings 242 are configured to receive the fasteners 210 used to secure the nut plate assembly 100 to one of the mounting structures 150, such as the wing ribs 138 (shown in Figure 4 ).
  • the nut plate assembly 100 is devoid of channel fittings 202 at the mounting area 240 allowing the bottom 224 of the base plate 200 to be mounted to the wing ribs 138.
  • the base plate 200 includes a first mating area 246 extending between the mounting area 240 and the first side 226.
  • the base plate 200 includes a second mating area 248 extending between the mounting area 240 and the second side 228.
  • the first mating area 246 has a plurality of the base plate openings 220 and a plurality of the channel fittings 202 coupled to the base plate 200 at the first mating area 246.
  • the second mating area 248 has a plurality of the base plate openings 220 and a plurality of the channel fittings 202 coupled to the base plate 200 at the second mating area 248.
  • the first mating area 246 is configured to be cantilevered from the mounting structure 150 (for example, the wing ribs 138) and extend to the first side 226.
  • the first side 226 may face a second side of an adjacent nut plate assembly (not shown) within the wing assembly 116.
  • the second mating area 248 is configured to be cantilevered from the mounting structure 150 and extend to the second side 228.
  • the second side 228 may face a first side of an adjacent nut plate assembly (not shown) within the wing assembly 116.
  • Figure 6 is a side view of the channel fitting 202 in accordance with an example.
  • Figure 7 is an end view of the channel fitting 202 in accordance with an example.
  • the channel fitting 202 is used to hold the nut cap 204 (shown in Figure 8 ).
  • the channel fitting 202 may be manufactured from a lightweight material to avoid causing sagging of the base plate 200 when mounted to the mounting structure 150 (shown in Figure 4 ).
  • the channel fitting 202 may be manufactured from a material having sufficient strength and/or rigidity to provide structural support for the base plate 200.
  • the channel fitting 202 may be manufactured from a glass fiber reinforced injection molded plastic, such as polyether ether ketone (PEEK), polyamide, polyimide, and the like.
  • PEEK polyether ether ketone
  • the channel fitting 202 includes a main body 250 having a top 252 and a bottom 254.
  • the channel fitting 202 includes a first side wall 256 extending from the bottom 254 and a second side wall 258 extending from the bottom 254.
  • the channel fitting 202 includes a nut cap channel 260 between the side walls 256, 258 that receives the nut cap 204.
  • the nut cap channel 260 is located below the bottom 254 of the main body 250.
  • the channel fitting 202 includes a first rail 262 extending from the first side wall 256 into the nut cap channel 260 and a second rail 264 extending from the second side wall 258 into the nut cap channel 260.
  • the nut cap channel 260 includes a first groove 266 between the first rail 262 and the main body 250 and a second groove 268 between the second rail 264 and the main body 250.
  • the nut cap 204 is configured to be received in the first groove 266 and the second groove 268.
  • the nut cap channel 260 is open at the front of the channel fitting 202 to receive the nut cap 204 through the open front.
  • the nut cap channel 260 may be open at the rear of the channel fitting 202 or may be open from above or from below to receive the nut cap 204.
  • the first and second rails 262, 264 may include notches 269 (shown in phantom) configured to receive a portion of the nut cap 204 or a retaining ring for the nut cap 204.
  • the channel fitting 202 includes one or more openings 270 through the main body 250 configured to receive the fastener 210 (shown in Figure 5 ).
  • the opening 270 passes through the main body 250 between the top 252 and the bottom 254.
  • the channel fitting 202 includes a pair of openings 270, with one of the openings 270 positioned closer to a front 272 of the main body 250 and the other opening 270 positioned closer to a rear 274 of the main body 250.
  • the channel fitting 202 may include greater or fewer openings 270 in alternative examples.
  • the channel fitting 202 includes a rim 276 surrounding the opening 270.
  • the rim 276 may be elevated above the top 252 of the main body 250, such as to extend into the base plate 200 (shown in Figure 5 ).
  • the channel fitting 202 includes a rim seal 278 around the edge of the rim 276 to seal the channel fitting 202 to the mounting structure 150 (shown in Figure 4 ).
  • the rim seal 278 may be separate rim seal, such as an O-ring or gasket coupled to the rim 276.
  • the rim seal 278 may be integral with the channel fitting 202, such as co-molded with the main body 250.
  • the rim 276 may be thin at the edge to form a compressible or deformable rim seal.
  • the channel fitting 202 includes a front support wall 280 at the front 272.
  • the front support wall 280 extends upward from the top 252 of the main body 250.
  • the front support wall 280 is configured to engage and provide support to the reinforcement lip 234 (shown in Figure 5 ) of the base plate 200.
  • the front support wall 280 may have a curved profile (i.e. a curved wall) in various examples.
  • Figure 8 is a cross-sectional view of the nut cap 204 in accordance with an example.
  • the nut cap 204 extends between a top 282 and a bottom 284.
  • the nut cap 204 includes a flange 286 at the top 282 operating as a nut cap retainer.
  • the flange 286 is configured to be received in the first and second grooves 266, 268 of the nut cap channel 260 (shown in Figure 7 ).
  • the nut cap 204 includes a pocket 288 that receives the nut 208.
  • the pocket 288 is open at the top 282 and is closed at the bottom 284 by a base 289 of the nut cap 204.
  • the body of the nut cap 204 surrounds the pocket 288 around the outside of the pocket 288 and at the bottom of the pocket 288.
  • the base 289 isolates the nut 208 and the fastener 210 from the interior of the wing assembly 116 to operate as a spark arrest feature for static discharge.
  • the nut cap 204 includes a locating feature 290 for locating the nut 208 in the pocket 288.
  • the locating feature 290 engages the nut 208 to hold the nut 208 from moving in the pocket 288, such as for receiving the fastener 210 from above.
  • the locating feature 290 may be a surface of the pocket 288, such as a flat surface used to engage and hold the nut 208.
  • the locating feature 290 may be defined by a groove extending into the side wall of the nut cap 204 or a protrusion extending from the side wall of the nut cap 204 into the pocket 288 to engage the nut 208.
  • Figure 9 is a cross-sectional view of the channel fitting 202 and the nut caps 204 coupled to the channel fitting 202.
  • the nut caps 204 are aligned with the openings 270 in the channel fitting 202.
  • the flange 286 of each nut cap 204 is received in the nut cap channel 260, such as in the groove 266.
  • the rail 264 supports the flange 286 between the rail 264 and the bottom 254 of the main body 250.
  • a retaining ring 292 surrounds the nut cap 204 to retain the nut cap 204 in the nut cap channel 260.
  • the retaining ring 292 is received in the notch 269 (shown in Figures 6 and 7 ).
  • the pocket 288 of the nut cap 204 When assembled, the pocket 288 of the nut cap 204 is aligned with the opening 270 in the main body 250.
  • the nut 208 is received in the pocket 288.
  • the nut 208 is located in the pocket 288 by the locating feature 290.
  • the nut 208 includes a nut seal 294 at a top of the nut 208.
  • the nut seal 294 may be at least partially received in the pocket 288 and/or may be at least partially received in the opening 270.
  • the nut seal 294 may extend into the rim 276, such as being coplanar with the rim seal 278.
  • the nut seal 294 may be sealed to the nut cap 204 and/or the main body 250 of the channel fitting 202 and/or the mounting structure 150 (shown in Figure 4 ).
  • Figure 10 is a side cross-sectional view of the nut plate assembly 100 mounted to the mounting structures 150.
  • Figure 11 is a perspective, partial sectional view of the nut plate assembly 100 mounted to the mounting structures 150.
  • the nut plate assembly 100 is coupled to the spar flange 144 of the wing spar 132 and the wing panel 130.
  • the channel fitting 202 is coupled to the base plate 200.
  • the front support wall 280 extends along and provides support for the reinforcement lip 234.
  • the nut caps 204 and the openings 270 in the channel fitting 202 are aligned with the base plate openings 220 to receive the fasteners 210.
  • the fasteners 210 are used to securely couple the wing panel 130 to the wing spar 132.
  • the wing panel 130 includes an inner surface 160 and an outer surface 162.
  • the inner surface 160 may be a bottom surface of the wing panel 130 and the outer surface 162 may be a top surface of the wing panel 130.
  • the wing panel 130 forms an exterior structure of the wing assembly 116 such that the outer surface 162 of the wing panel 130 defines an exterior surface 163 of the wing assembly 116.
  • the fasteners 210 are configured to be coupled to the wing panel 130 from the exterior surface of the wing assembly 116.
  • the wing panel 130 includes wing panel openings 164 extending therethrough between the inner surface 160 and the outer surface 162.
  • the wing panel openings 164 may be chamfered at the outer surface 162 to countersink or flush mount the fasteners 210 and the wing panel openings 164.
  • the spar flange 144 of the wing spar 132 includes an inner surface 170 and an outer surface 172.
  • the inner surface 170 may be a bottom surface of the spar flange 144 and the outer surface 172 may be a top surface of the spar flange 144.
  • the wing spar 132 is positioned interior of the wing panel 130 such that the outer surface 172 of the spar flange 144 faces the inner surface 160 of the wing panel 130.
  • the spar flange 144 of the wing spar 132 includes spar flange openings 174 therethrough between the inner surface 170 and the outer surface 172.
  • the spar flange openings 174 are aligned with the wing panel openings 164.
  • the spar flange 144 extends to a spar flange edge 176.
  • the nut plate assembly 100 is positioned relative to the mounting structures 150 such that the base plate openings 220, the openings 270 and the nut caps 204 are aligned with the spar flange openings 174 and the wing panel openings 164 to receive the fasteners 210.
  • the reinforcement lip 234 at the front edge 230 extends forward of the spar flange edge 176 to form the seal groove 236.
  • the reinforcement lip 234 and the front support wall 280 provide structural stiffness for the base plate 200, such as to prevent sagging or drooping of the base plate 200 away from the mounting structures 150 prior to installing the fasteners 210.
  • the top 222 of the base plate 200 faces the inner surface 170 of the spar flange 144 of the wing spar 132.
  • the nut plate assembly 100 is located below the mounting structures 150 at the interior of the wing assembly 116.
  • the nut plate assembly 100 positions the nuts 208 for mating with the fasteners 210, which are installed from the exterior surface of the wing assembly 116.
  • the nut caps 204 enclose the pockets 288 to retain the nuts 208 therein and to provide spark arresting features to isolate the fasteners 210 and the nuts 208 from the interior of the wing assembly 116.
  • the seal groove 236 receives the base plate seal 206 between the base plate 200 and the mounting structures 150.
  • the base plate seal 206 is sealed to the base plate 200, the spar flange 144 of the wing spar 132 and the wing panel 130.
  • the base plate seal 206 may have a seal interface against the top 222 of the base plate 200 and/or against the reinforcement lip 234, a seal interface against the spar flange edge 176 and/or against the inner surface 170 of the spar flange 144, and a seal interface against the inner surface 160 of the wing panel 130.
  • the base plate seal 206 may be sealed against other surfaces of the mounting structures 150 in alternative examples.
  • the base plate seal 206 may be compressed against the spar flange edge 176 and/or the inner surface 160 of the wing panel 130.
  • the rims 276 of the channel fitting 202 may extend into the base plate openings 220.
  • the rims seals 278 may seal against the inner surface 170 of the spar flange 144 of the wing spar 132.
  • the rims seals 278 may be compressed against the inner surface 170 of the spar flange 144.
  • the nut seals 294 are sealed to the fasteners 210 and/or the nut caps 204 and/or the main body 250 of the channel fitting 202.
  • the nut seals 294 may be compressed against the channel fitting 202 and/or the nut caps 204 when the fasteners 210 are tightened to the nuts 208.
  • the base plate seal 206 and/or the rim seal 278 and/or the nut seal 294 seal the interior structures and compartments of the wing assembly 116 from the exterior surface of the wing assembly 116.

Claims (15)

  1. Mutterplattenanordnung (100), die aufweist:
    eine Grundplatte mit einer Oberseite (222) und einer Unterseite (224), wobei die Oberseite (222) eingerichtet ist, einer Innenfläche (160) einer Befestigungsstruktur (150) zugewandt zu sein, wobei die Grundplatte (200) hindurchgehende Grundplattenöffnungen (220) aufweist, wobei die Grundplatte (200) eine erste Seite (226) und eine zweite Seite (228) aufweist, wobei die Grundplatte (200) einen vorderen Rand (230) und einen hinteren Rand (232) aufweist, wobei die Grundplatte (200) eine Verstärkungslippe (234) bei der vorderen Kante (230) der Grundplatte (200) aufweist, wobei die Verstärkungslippe (234) nicht koplanar zur Grundplatte (200) ist und sich zwischen der ersten Seite (226) und der zweiten Seite (228) erstreckt;
    Kanalbefestigungen (202), die an den Boden (224) der Grundplatte (200) gekoppelt sind, wobei jede Kanalbefestigung (202) einen Hauptkörper (250) mit einer Oberseite (252) und einer Unterseite (254) aufweist, wobei die Oberseite (252) des Hauptkörpers (250) der Unterseite (224) der Grundplatte (200) zugewandt ist, wobei der Hauptkörper (250) eine Öffnung (270) aufweist, die mit einer entsprechenden Grundplattenöffnung (220) der Grundplattenöffnungen (220) in der Grundplatte (200) ausgerichtet ist, wobei die Kanalbefestigung (202) einen Mutterkappenkanal (260) bei der Unterseite (254) des Hauptkörpers (250) aufweist, der mit der Öffnung (270) im Hauptkörper (250) ausgerichtet ist; und
    Mutterkappen (204), die an die Kanalbefestigungen (202) gekoppelt sind und die unterhalb der Unterseite (254) des Hauptkörpers (250) positioniert sind, wobei die Mutterkappen (204) in den Mutterkappenkanälen (260) der Kanalbefestigungen (202) aufgenommen sind, wobei jede Mutterkappe (204) eine Tasche (288) aufweist, die bei einer Oberseite (282) der Mutterkappe (204) offen ist, wobei die Tasche (288) derart ist, dass sie eine Mutter (208) mit der Öffnung (270) in dem Hauptkörper (250) und der entsprechenden Grundplattenöffnung (220) ausgerichtet hält, um eine Befestigungseinrichtung (210) aufzunehmen, die zum Sichern der Grundplatte (200) an einer Befestigungsstruktur (150) von einer äußeren Fläche (163) der Befestigungsstruktur (150) durch die Grundplatte (200) und den Hauptkörper (250) einer Kanalbefestigung (202) der Kanalbefestigungen (202) verwendet wird,
    wobei jede Kanalbefestigung (202) eine vordere Stützwand (280) umfasst, um in die Verstärkungslippe (234) einzugreifen, um die Verstärkungslippe (234) zu stützen, und wobei die Verstärkungslippe eine gekrümmte Wand ist, die sich von der Grundplatte (200) bei dem vorderen Rand (230) erstreckt.
  2. Mutterplattenanordnung (100) nach Anspruch 1, wobei jede Mutterkappe (204) eine Basis (289) unterhalb der Tasche (288) umfasst, die einen geschlossenen Boden zum Zurückhalten einer Mutter (208) in der Tasche (288) ausbildet.
  3. Mutterplattenanordnung (100) nach Anspruch 1 oder 2, wobei jede Mutterkappe (204) ein Lokalisierungsmerkmal (290) in der Tasche (288) zum Eingreifen in eine Mutter (208) zum Verhindern einer Bewegung der Mutter (208) in der Tasche (288) umfasst, um eine Befestigungseinrichtung (210) von einer äußeren Fläche (163) einer Befestigungsstruktur (150) auszunehmen.
  4. Mutterplattenanordnung (100) nach einem der Ansprüche 1 bis 3, wobei die Verstärkungslippe (234) eine Dichtungsnut (236) ausbildet, wobei die Mutterplattenanordnung (100) ferner eine Grundplattendichtung (206) aufweist, die in der Dichtungsnut (236) aufgenommen ist.
  5. Mutterplattenanordnung (100) nach einem der Ansprüche 1 bis 4, die eine Mutter (208) aufweist und wobei die Mutter (208) eine Mutternut (294) umfasst, die zum Abdichten zumindest einer Befestigungseinrichtung (210) und/oder des Hauptkörpers (250) der Kanalbefestigung (202) eingerichtet ist.
  6. Mutterplattenanordnung (100) nach einem der Ansprüche 1 bis 5, wobei die Kanalbefestigung (202) einen Rand (276) um die Öffnung (270) herum umfasst, wobei die Kanalbefestigung (202) eine Randdichtung (278) um den Rand (276) herum umfasst, die zum Abdichten einer inneren Fläche (160) einer Befestigungsstruktur (150) eingerichtet ist.
  7. Mutterplattenanordnung (100) nach einem der Ansprüche 1 bis 6, die ferner eine Grundplattendichtung (206) aufweist, die eingerichtet ist, zwischen der Oberseite (222) der Grundplatte (200) und einer inneren Fläche (160) einer Befestigungsstruktur (150) positioniert zu werden, wobei die Kanalbefestigungen (202) in einem beabstandeten Verhältnis entlang der Grundplatte mit Spalten (212) zwischen den Kanalbefestigungen angeordnet sind.
  8. Mutterplattenanordnung (100) nach einem der Ansprüche 1 bis 7, wobei die Grundplatte (200) einen ersten Eingriffsbereich (246) und einen zweiten Eingriffsbereich (248) umfasst, wobei der erste Eingriffsbereich (246) eine Vielzahl der Grundplattenöffnungen (220) und eine Vielzahl der Kanalbefestigungen (202) darin aufweist, wobei der zweite Eingriffsbereich (248) eine Vielzahl der Grundplattenöffnungen (220) und eine Vielzahl der Kanalbefestigungen (202) darin aufweist, wobei die Grundplatte (200) einen Befestigungsbereich zwischen den ersten und zweiten Eingriffsbereichen (246, 248) umfasst, wobei der Befestigungsbereich eingerichtet ist, an einer zweiten Befestigungsstruktur (150) befestigt zu werden, wobei der erste Eingriffsbereich (246) eingerichtet ist, freitragend von einer zweiten Befestigungsstruktur (150) und dem ersten Eingriffsbereich (246) zu sein, der sich von der ersten Seite aus erstreckt, wobei der zweite Eingriffsbereich (248) eingerichtet ist, von einer zweiten Befestigungsstruktur (150) und freitragend zu sein, und wobei sich der zweite Eingriffsbereich (248) zur zweiten Seite erstreckt.
  9. Mutterplattenanordnung (100) nach einem der Ansprüche 1 bis 8, wobei jeder Mutterkappenkanal (260) auf einer Vorderseite von jeder Kanalbefestigung (202) offen ist, um jede Mutterkappe (204) aufzunehmen.
  10. Mutterplattenanordnung (100) nach einem der Ansprüche 1 bis 9, wobei jeder Mutterkappenkanal (260) eine erste Schiene (262), die eine erste Nut (266) definiert, und eine zweite Schiene (264) umfasst, die eine zweite Nut (268) definiert, wobei jede Mutterkappe (204) einen Flansch (286) bei der Oberseite (282) der Mutterkappe umfasst, um in den ersten und zweiten Nuten aufgenommen zu werden und um durch die ersten und zweiten Schienen (262, 264) gestützt zu werden, und wobei jede Mutterkappe ferner eine Mutterkappen-Rückhalteeinrichtung aufweist, die an die ersten und zweiten Schienen gekoppelt ist, um die Mutterkappe an den ersten und zweiten Schienen zu sichern.
  11. Mutterplattenanordnung (100) nach einem der Ansprüche 1 bis 10, wobei sich jeder Hauptkörper (250) zwischen einer Vorderseite (272) und einer Rückseite (274) erstreckt, wobei die Öffnung (270) entlang des Hauptkörpers (250) näher zur Vorderseite (272) als zur Rückseite (274) positioniert ist, wobei jeder Hauptkörper (250) ferner eine zweite Öffnung (270) entlang des Hauptkörpers (250) näher zur Rückseite (274) als zur Vorderseite (272) aufweist und mit einer entsprechenden Grundplattenöffnung (220) ausgerichtet ist, um eine zweite Befestigungseinrichtung (210) aufzunehmen, wobei jede Mutterkappe (204) mit der Öffnung (270) und der zweiten Öffnung (270) ausgerichtet ist.
  12. Mutterplattenanordnung (100) nach Anspruch 2, wobei die Mutterkappe (204) nichtleitend ist.
  13. Mutterkappenanordnung (100) nach Anspruch 11, die ferner einen Rückhaltering (292) aufweist, der die Mutterkappe (204) umgibt, um sie in dem Mutterkappenkanal (260) zurückzuhalten.
  14. Flügelanordnung (116), die aufweist:
    einen Flügelholm (132) mit einem Holmflansch (144), der eine Innenfläche (160) und eine Außenfläche (162) umfasst, wobei der Holmflansch (144) Holmflanschöffnungen (174) aufweist;
    eine Flügelplatte (130) mit einer Innenfläche (170) und einer Außenfläche (172), wobei die Innenfläche (170) der Flügelplatte (130) der Außenfläche (162) des Holmflanschs (144) zugewandt ist, wobei die Flügelplatte (130) Flügelplattenöffnungen (164) aufweist, die mit den Holmflanschöffnungen (174) ausgerichtet sind;
    eine Mutterplattenanordnung (100) gemäß einem der Ansprüche 1 bis 13, wobei sich die Mutterplattenanordnung (100) entlang der Innenfläche (160) des Holmflanschs (144) erstreckt, wobei die Oberseite (222) der Grundplatte (200) der Innenfläche des Holmflanschs (144) zugewandt ist und wobei die Grundplattenöffnungen (220) mit den Holmflanschöffnungen (174) ausgerichtet sind; und
    Befestigungseinrichtungen (210), die durch die Flügelplattenöffnungen (164), die Holmflanschöffnungen (174) und die Hauptkörperöffnungen (270) in den Mutterkappen (204) von einer Außenfläche (163) der Flügelplatte (130) aus verlaufen, wobei die Befestigungseinrichtungen (210) an entsprechenden Muttern (208) der Mutterplattenanordnung (100) gesichert sind, um die Flügelplatte (130) an dem Holmflansch (144) zu sichern.
  15. Flügelanordnung (116) nach Anspruch 14, die ferner eine Flügelrippe (138) mit einer Befestigungsfläche nahe einem Ende der Flügelrippe (138) aufweist, wobei das Ende der Flügelrippe (138) dem Flügelholm (132) zugewandt ist, wobei die Unterseite (224) der Grundplatte (200) an der Befestigungsfläche der Flügelrippe (138) befestigt ist, wobei die Unterseite (224) der Grundplatte (200) sich von einer ersten Seite der Flügelrippe (138) zur ersten Seite (226) der Grundplatte (200) erstreckt, wobei die Unterseite (224) der Grundplatte (200) sich von einer zweiten Seite der Flügelrippe (138) zur zweiten Seite (228) der Grundplatte (200) erstreckt.
EP20190055.2A 2019-08-12 2020-08-07 Mutterplattenanordnung Active EP3778379B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US16/537,805 US11268562B2 (en) 2019-08-12 2019-08-12 Nut plate assembly

Publications (2)

Publication Number Publication Date
EP3778379A1 EP3778379A1 (de) 2021-02-17
EP3778379B1 true EP3778379B1 (de) 2023-10-04

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EP20190055.2A Active EP3778379B1 (de) 2019-08-12 2020-08-07 Mutterplattenanordnung

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US (1) US11268562B2 (de)
EP (1) EP3778379B1 (de)
CN (1) CN112389673A (de)
AU (1) AU2020213403A1 (de)
CA (1) CA3088759C (de)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11624395B2 (en) * 2020-10-22 2023-04-11 D Three Enterprises, Llc Channel strut fasteners

Family Cites Families (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2299158A (en) 1941-02-18 1942-10-20 Richard W Luce Gang channel fastener
US2879820A (en) * 1955-05-31 1959-03-31 Boots Aircraft Nut Corp Narrow gang channel support and positioning means for securing nuts
US3020946A (en) 1957-02-28 1962-02-13 Elastic Stop Nut Corp Anchor unit with spherical surface to permit angular movement
US3164191A (en) 1960-10-12 1965-01-05 Kaynar Mfg Co Snap-out fastener and channel assembly
US3483910A (en) * 1968-04-01 1969-12-16 Youngstown Sheet And Tube Co Attachment devices including extend working means,for apertured structural members
US3669171A (en) * 1970-06-08 1972-06-13 Morris Yavitch Fastener assembly
GB1537473A (en) * 1975-10-29 1978-12-29 Btr Industries Ltd Structural assemblies
US4488844A (en) 1982-06-07 1984-12-18 Jacobson Mfg. Co., Inc. Floating fastener retainer assembly with removable fasteners
US4790701A (en) 1987-05-08 1988-12-13 Jacobson Mfg. Co., Inc. Floating fastener retainer assembly with removable fasteners
US4895484A (en) 1988-10-25 1990-01-23 Deutsch Fastener Corp. Fastener with floating nut for use with composite structure
US4948313A (en) * 1988-11-23 1990-08-14 Wesanco, Inc. Nut platform for framing channels
DE4421252A1 (de) * 1994-06-17 1995-12-21 Hilti Ag Befestigungsvorrichtung
US6146071A (en) * 1999-04-14 2000-11-14 Illinois Tool Works, Inc. Caged nut assembly
DE10301018B4 (de) * 2003-01-13 2005-07-28 Progress-Werk Oberkirch Ag Anordnung zum Verbinden eines rohrförmigen ersten Bauteils mit einem zweiten Bauteil sowie Verfahren zur Herstellung einer solchen Anordnung
DE602006020443D1 (de) * 2005-06-03 2011-04-14 Fatigue Technology Inc Befestigungseinrichtung und Verfahren zum Zusammensetzen derselben
US8277158B2 (en) 2007-11-15 2012-10-02 The Monadnock Company Floating nut plate
FR2983268B1 (fr) 2011-11-30 2014-11-21 Airbus Operations Sas Dispositif de fixation muni d'un systeme de protection d'une piece annexe et procede d'utilisation associe
US8911191B2 (en) * 2012-01-24 2014-12-16 The Boeing Company Self-indexing nut plate
US9083169B2 (en) 2012-01-24 2015-07-14 The Boeing Company Self-indexing nut plate
US9719547B2 (en) 2013-03-21 2017-08-01 The Boeing Company Anti-rotation rivetless nut plate
US10179640B2 (en) * 2016-08-24 2019-01-15 The Boeing Company Wing and method of manufacturing

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Publication number Publication date
US11268562B2 (en) 2022-03-08
EP3778379A1 (de) 2021-02-17
AU2020213403A1 (en) 2021-03-04
US20210048058A1 (en) 2021-02-18
CN112389673A (zh) 2021-02-23
CA3088759C (en) 2024-01-16
CA3088759A1 (en) 2021-02-12

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